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WO1979000037A1 - Projectile avec canaux de circulation provoquant une rotation - Google Patents

Projectile avec canaux de circulation provoquant une rotation Download PDF

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Publication number
WO1979000037A1
WO1979000037A1 PCT/DE1978/000008 DE7800008W WO7900037A1 WO 1979000037 A1 WO1979000037 A1 WO 1979000037A1 DE 7800008 W DE7800008 W DE 7800008W WO 7900037 A1 WO7900037 A1 WO 7900037A1
Authority
WO
WIPO (PCT)
Prior art keywords
projectile
swirl
channels
axis
channel group
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/DE1978/000008
Other languages
German (de)
English (en)
Inventor
J Ballmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of WO1979000037A1 publication Critical patent/WO1979000037A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/26—Stabilising arrangements using spin

Definitions

  • the invention relates to a projectile, in particular for firing from a smooth tube, with guide parts and / or a sabot or without such additional parts, equipped with swirl-producing flow channels which have a tapering part on the inlet side with a subsequent constriction and, downstream thereafter, an extension part in which the propellant gas Have reached supersonic speed.
  • the projectile according to the invention can be one with a full story body or with a tubular story body. It can also be designed with or without a tail unit.
  • the projectile according to the invention has guide parts, these can consist in a known manner of a cage or of rings, of which or which the projectile body form is conclusively surrounded.
  • the cage and the rings then preferably consist of a plurality of segments which are detachably or only connected to one another by predetermined breaking points.
  • the sabot of the projectile if present, is arranged as usual between the front end of the propellant container and the rear part of the projectile body, without being permanently connected to it. It can have one or more parts. It is also possible to combine it with the guide parts to form a unit.
  • Projectiles of the type in question are not only intended for sniping, but are also used to a large extent as so-called practice projectiles for target practice.
  • the twist is used in particular for the flight stability of the projectiles.
  • the speed of rotation around the longitudinal axis of the projectile also called speed, is determined by the shape and the mass geometry of the projectile body.
  • projectiles of the type mentioned can be swirled in the launch tube by equipping them with so-called swirl trains.
  • the projectiles have a slight excess at least on part of their lateral surface, so that when they are fired they are first pressed into the swirl trains and then follow the swirl trains almost positively.
  • the height of the swirl is determined by the swirl angle of the pipe and the speed of the projectiles. This fact prevents any possibility of twist tuning if you have different projectile shapes from the same tube shoot or want to achieve different exit speeds, as is particularly desirable in practice shooting, but may also be desired in sharp shooting. The result is incorrect flight and target behavior of the projectile body.
  • projectile shapes have also become known in which the projectiles are made in one piece and are equipped with so-called swirl ducts along their outer wall or inside. These swirl channels are flowed through by the propellant gases during firing and enable swirl projectiles to be fired from smooth pipes. By appropriate channel design, they also allow the speed of the projectiles to be selected independently of the speed at which they fire for the same launch tube.
  • the known projectile designs in question have not prevailed because of their external ballistic problems and because of an unfavorable design of their swirl channels.
  • the projectile twist is generated in that the part of the propellant gases which overtakes the projectile on the way through the swirl channels is given a velocity component in the circumferential direction by the projectile, which leads to an opposing speed of the projectile.
  • the swirl ducts of known projectiles are, on the one hand, ducts running spirally around the projectile axis with a constant or tapering cross section, in which the propellant gas can flow at the speed of sound at the most.
  • a projectile with swirl ducts has already become known, which expand again after a tapering part and a constriction, so that the gas in the projectile tube in the expansion part reaches supersonic speed (DT-PS 597 633).
  • the gas only gets its peripheral speed after it has reached supersonic speed at a so-called called baffle, which is located at the rear end of the channels on one side of the channels and is inclined to the flow.
  • the invention is based on the object of a projectile of the type mentioned with swirl-generating flow channels which allow it to be fired with a swirl, the speed of which can be selected independently of the height of the projectile exit speed, and stabilization and a flight adapted to the ballistic requirements causes its projectile body to train so that this twist is achieved with the least possible losses.
  • the respective channel axis of the swirl channels in their extension part rectilinear or moderately curved, skewed at a distance from the axis of the projectile, and in order to avoid compression shocks, the channel walls of the extension part, seen in the flow direction, are convex and / or have a straight shape and / or a shape which is at most slightly concavely curved.
  • the swirl-generating flow channels or swirl channels are flowed through by the propellant gas when the projectile according to the invention is fired and then bring about the desired swirl generation.
  • the propellant gas flowing through the swirl channels is forced by the boundaries of the swirl channels to change the swirl around the pipe axis, that is to say to change its flow velocity in the pipe circumferential direction.
  • the arrangement and design of the swirl channels provided according to the invention ensures a particularly high degree of utilization of the energy of the propellant gases for the swirl generation.
  • the course of the axis and the shape of the walls of the swirl channels, as provided by the invention, are controlled by the requirement that no or only very weak compression shocks occur in the swirl channels and negligible in terms of the losses caused by them, and that the propellant gas also coexists with the swirl channels leaves the highest possible supersonic speed and, based on the projectile axis, with the greatest possible twist.
  • the axis of the swirl channels at the channel outlet is arranged as far as possible from the pipe axis in the new projectile and is directed in such a way that the highest possible circumferential component of the gas velocity results.
  • the walls of the swirl channels in their extension part have the shape already mentioned for this purpose, since this compression shock completely or almost completely prevents them.
  • the swirl channels each have an axis which is curved continuously or discontinuously in the tapering part thereof. Possibly. there is then an additional swirl generation by the deflection and the associated Change of direction of the propellant gases in the tapered part of the swirl channels.
  • the pressure-side part of its wall has an extension at the outflow end of the swirl ducts. This extension then increases the speed component of the propellant gas in the pipe circumferential direction and thus further promotes the swirl generation.
  • its swirl channels can each have an axis which runs at a constant or only slightly different distance from the projectile axis. Possibly. the swirl channels represent axial channels.
  • the axes of the swirl ducts greatly change their distance from the projectile axis from their inflow end to their outflow end and are designed to flow from the inside to the outside or vice versa.
  • the swirl channels then represent radial channels.
  • the projectile according to the invention it can further be provided that it has swirl channels which are arranged in a ring surrounding the projectile axis and form an axial channel group. Furthermore, the projectile according to the invention can have swirl channels which are arranged such that they surround the projectile axis in a ring shape and form a radial channel group. Finally, in the case of the projectile according to the invention, it is also possible for two or more channel groups which are spaced apart and flowed through in succession to be provided for two-stage or multi-stage swirl generation. The execution of the projectile with two or more channel groups spaced apart from one another and flowed through in succession for a two- or multi-stage swirl generation is particularly effective.
  • the propellant gas After the propellant gas has escaped from a channel group, it is decelerated from supersonic to subsonic speed by friction on the surrounding walls between the channel groups before it enters the next channel group.
  • the pressure recovery thus created is available again for the swirl generation that follows in the next stage.
  • the deceleration of the propellant gas between the channel groups is associated with an increase in entropy due to the compression surges and friction.
  • the maximum possible mass flow related to the area flowed through that is to say the so-called critical current density
  • the critical current density is reduced; the critical current density always occurs in the vicinity of the narrowest point of the channel when it is reached in a channel.
  • This also applies to a channel group or swirl generation stage, in which the so-called narrowest stage cross section corresponds to the narrowest total flow cross section of all swirl channels of the stage including all leakage passages.
  • the critical current density, as described, decreasing in the direction of flow is taken into account according to the invention in such embodiments of the projectile by the fact that the narrowest overall cross-section of the group of channels formed by the individual channels of a channel group increases downstream from channel group to channel group.
  • the increase should be such that the highest possible swirl effect is achieved based on the amount of gas used for swirl generation.
  • the increase in the overall channel group cross section is achieved in that the individual channels of a subsequent channel group each have a larger cross section than the individual channels of a channel group located in front of this channel group.
  • Another embodiment provides for this that, with the same cross-section of the individual channels of all channel groups, a following channel group has more channels than a channel group located in front of this channel group.
  • the channel groups downstream are provided with leakage passages which increase in size from channel group to channel group.
  • the amount of gas used for the swirl generation of the projectile according to the invention can be kept much smaller overall than in the already known projectiles with swirl channels, so that the amount of gas used for swirl generation as propellant gas loss is only moderate due to the design and arrangement of the swirl channels, swirl channel groups and swirl generation stages Has an influence on the exit velocity of the projectile.
  • the projectile according to the invention is also intended in particular for firing from a smooth tube, however, it is also suitable for being fired from a tube provided with twist trains.
  • the invention also provides that its projectile body or its guide parts and its sabot have such an undersize that its swirl is not determined by the swirl pulls of the tube.
  • FIG. 8 shows a sub-caliber tubular projectile in a tube in partial representation, partly in plan view and partly in sectional view,
  • FIG. 9 shows the guide parts of the projectile shown in FIG. 8 in an end view
  • Fig. 10 the projectile body in a tube of a calibrated full floor, partly in plan view and partly in sectional view, and
  • Fig. 11 shows the projectile body shown in Fig. 10 in cross section along line A-B thereof.
  • Swirl channels of the type shown in FIGS. 1 to 7 can be arranged in or on the projectile body. However, they can also be located in the guide parts and / or the sabot of the projectile, if such parts are provided.
  • the swirl channels are all designated by the reference number 20, while the parts of the projectile in which they are located have the reference number 21.
  • the projectile axis is indicated in FIGS. 1 and 2 by dash-dotted line 22.
  • the axis of the swirl channels is designated 23 in each case. 1 and 2, the line 24 indicates the distance between the swirl channel axis 23 and the projectile axis 22.
  • All of the swirl channels 20 shown in FIGS. 1 to 7 have different cross sections over their length.
  • the swirl channels 20 have a tapering cross section on the inlet side, as a result of which a tapering part 25 is formed.
  • a constriction 26 adjoins this taper part. This constriction 26 is followed by an expansion of the cross section of the swirl channels 20, whereby an expansion part 27 thereof is formed.
  • the walls of the swirl channels 20 shown in FIGS. 1 and 2 are initially convex in their extension part 27 following the constriction 26 and then have a straight shape.
  • the swirl channel shown in FIG. 1 has a rectilinear axis 23 which is skewed to the projectile axis 22 at only a slightly different distance. With this swirl channel, a constant change in its cross section takes place within its tapering part 25, its constriction 26 and its extension part 27.
  • the axis 23 also has a rectilinear shape in the region of its extension part 27. In the area of its tapered part 25 and up to its constriction 26, however, the axis 23 is curved. Viewed overall, however, the axis 23 is also arranged in this swirl channel 20 at only a slightly different distance and essentially skew to the projectile axis 22. Its cross-section also changes continuously in the region of its tapering part 25, its constriction 26 and its extension part 27.
  • the swirl channel 20 of FIG. 3 has an axis 23 which corresponds in terms of its design and arrangement to the axis of the swirl channel 20 of FIG. 1. In contrast to the swirl duct of FIG.
  • the swirl duct of FIG. 3 has a discontinuous change in its cross section in the region of its taper part 25, its constriction 26 and its extension part 27, in particular at the transitions from the taper part 25 to the constriction 26 and from the constriction 26 to the extension part 27.
  • the cross section in the region of the constriction 26 is constant as such.
  • FIG. 4 shows a swirl channel 20 with an axis 23 which extends in a straight line in the region of the extension part 27 and the constriction 26 and is otherwise arranged there corresponding to the axis of the swirl channel of FIG. 2.
  • the axis 23 of the swirl channel of FIG. 4 has a kink in its tapering part 25, due to which the swirl channel axis is there in a parallel position to the projectile axis.
  • its cross section changes continuously over its length, in particular in the region of its tapering part 25 and at the transitions from the tapering part 25 to the constriction 26 and from the constriction 26 the extension part 27.
  • the swirl channel in the region of the constriction 20 as such likewise has a constant cross section.
  • the swirl generation is based exclusively on the expansion of the propellant gas in this and its associated acceleration and swirl change around the projectile axis 22.
  • the swirl generation additionally has its own The reason for a change in direction of the flow of the propellant gas by deflection in the region of its tapering part 25.
  • the circles drawn in FIG. 2 illustrate how the propellant gas flowing through the swirl duct 20 expands to the speed of sound in the tapering part 25 up to the constriction 26 and then further accelerates to supersonic speed in the extension part 27.
  • the propellant gas is deflected in the tapering part 25 of the swirl duct 20, but can flow through the extension part 27 unhindered and without deflection and can exit from it.
  • the swirl channels of FIGS. 5 to 7 are those with the special feature that the pressure-side part of their wall has an extension 28 at its outflow end and thus in the region of its extension part 27.
  • this extension 28 can have different designs. Thus, it can pass into a wall part 29 that is adapted to it and opposite it, which then results in a trumpet-like outflow end of the swirl channel 20. Furthermore, it can have a half-shell-like configuration, as shown in FIG. 6, as a result of which the swirl channel 20 then has a beak-like shape at its outflow end. Finally, according to FIG. 7, it can also be designed in the form of a tongue.
  • the projectile G has a sub-caliber tubular projectile body 30.
  • a guide cage 31 is arranged in a form-fitting manner around the projectile body 30.
  • the guide cage 31 has a front guide ring 32 located near the front end of the projectile body 30, one at the rear end of the projectile body 30 provided rear guide ring 33 and a hollow cylindrical spacer 34 arranged between them.
  • the outer diameter of the guide rings 32, 33 corresponds to the caliber of the tube R, while the outer diameter of the spacer 34 is significantly smaller.
  • the rings 32, 33 and the spacer 34 of the guide cage 31 are composed of three longitudinal segments which are only connected by predetermined breaking points. A section of the guide rings 32, 33 and the spacer 34 is formed from each segment.
  • the guide cage 31 on the projectile body 30 For the form-fitting arrangement of the guide cage 31 on the projectile body 30, its segments are provided with longitudinal grooves 35.
  • the projectile body 30 has corresponding longitudinal grooves, not shown.
  • the form-fitting connection between the guide cage 31 and the projectile body 30 is established by means of parts, also not shown, which fit into the longitudinal grooves.
  • Swirl channels 20 are arranged both in the guide ring 32 and in the guide ring 33.
  • the swirl channels 20 have a configuration corresponding to FIG. 2.
  • a first group of axial channels is formed by the swirl channels 20 of the guide ring 33 and a second group by the swirl channels 20 of the guide ring 32.
  • a two-stage swirl generation therefore takes place through the two channel groups when the propellant gas flows through them.
  • a sabot 36 is provided following the rear end of the projectile body 30.
  • This sabot 36 lies with its front wall 37 against the E ⁇ dwandung 38 of the projectile body 30.
  • the sabot 36 has an annular outer shoulder 39. With this paragraph 39, it is still in contact against the rear end of the guide ring 33.
  • means not shown are provided, which ensure that they are held together before the projectile G is fired, but on the other hand, when the projectile body 30 exits the tube, the sabot 36 is separated from the one without further ado Projectile body 30 and the guide cage 31 allow.
  • the rear end of the sabot 36 extends approximately by the size of the half-floor caliber into the opening 40 of the propellant container 41 of the floor G.
  • the sabot 36 and the opening 40 of the propellant container 41 have a diameter which allows the swirl channels 20 of the guide ring 33 to be outside the area of the same.
  • the projectile body 30 is conveyed out of the pipe R by the propellant gas by means of the propellant mirror 36.
  • the propellant gas only acts on it. If the sabot 36 has passed through the opening 40 of the propellant container 41, the propellant gas also acts on the swirl channels 20, the swirl channels 20 of the first axial channel group located in the guide ring 53 first of the propellant gas and then the swirl channels 20 of those in the guide ring 32 flow through the second axial channel group.
  • the propellant gas gives the projectile body 30 and the guide cage 31 and the sabot 36 within the tube R the desired speed in the manner already described.
  • the centrifugal force acting on the guide cage 31 as a result of the rapidity causes a break in the predetermined break connecting its segments as well as a sideways flight of these segments.
  • the existing air resistance then separates the projectile body 30 from the sabot 36 and leaves the latter behind.
  • the projectile body 30 then travels with its intended trajectory on its own.
  • the body 42 of this projectile is composed of a main part 43, an intermediate part 44 and a head 45, which are screwed together by threads 46, 47 and of which the intermediate part 44 and the head 45 have a tapering cross section in the direction of the projectile tip.
  • On the main part 43 of the projectile body 42 are arranged at a distance from each other with this one-piece guide rings 48, 49.
  • a central bore 50 for the passage of propellant gas extends from the rear end to the front end of the main part 43 of the projectile body 42. At the entry end, this bore 50 is also provided with an extension 51.
  • the intermediate part 44 of the projectile body 42 has, following the bore 50 of the main part 43, a recess 52 which initially corresponds to this in terms of its diameter. In the direction of the front end of the projectile body 42, this recess 52 widens and merges into a group of radial swirl channels 20 which surround the projectile axis 32 in a ring shape and have a configuration corresponding approximately to FIG. 2.
  • the intermediate part 44 there is also an approximately conical projection 53 which is in a central arrangement and points with its tip in the direction of the projectile end. This projection 53 contributes to the formation of the swirl channels.
  • the projectile G shown in FIGS. 10 and 11 is transported out of the tube R when it is fired by the direct action of the propellant gas on its projectile body 45.
  • the propellant gas acts on the projectile body 45, it also enters the bore 50 and flows from the latter through the recess 52 and the swirl channels 20 into the space between the inner tube wall and the outer surface of the intermediate part 44 of the projectile body 45, from where it is then finally reaches the outlet opening of the tube R.
  • the propellant gas in the manner already described gives the projectile body 45 within the tube R the desired speed. After leaving the tube R, the projectile body 45 then describes its intended trajectory with the rapidity imparted to it.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Nozzles (AREA)
  • Testing Of Engines (AREA)

Abstract

Un projectile (G) comportant des canaux de circulation (20) qui provoquent sa rotation, concu particulierement pour le tir a l'aide d'une arme a feu a canon (R) non raye, comprend un corps (30) avec des elements de guidage (32, 33). Les elements de guidage (32, 33) comportent des canaux de circulation (20) dont la partie situee vers l'orifice d'entree, qui presente une section decroissante, est suivie d'un etranglement derniere lequel est situee une partie de section croissante, situee en aval. La circulation du gaz propulseur dans les canaux (20) exerce un effet de rotation sur le projectile (G). La ligne mediane des canaux de circulation, dans la partie de section croissante, est soit droite soit legerement incurvee, est espacee de l'axe (22) du projectile et forme un angle avec celui-ci. De plus, en aval, les parois internes de la partie de section croissante presentent une forme convexe et/ou droite ou, au plus, legerement concave.
PCT/DE1978/000008 1977-07-09 1978-07-03 Projectile avec canaux de circulation provoquant une rotation Ceased WO1979000037A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE2731092 1977-07-09
DE19772731092 DE2731092A1 (de) 1977-07-09 1977-07-09 Geschoss mit drall erzeugenden stroemungskanaelen

Publications (1)

Publication Number Publication Date
WO1979000037A1 true WO1979000037A1 (fr) 1979-02-08

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ID=6013540

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1978/000008 Ceased WO1979000037A1 (fr) 1977-07-09 1978-07-03 Projectile avec canaux de circulation provoquant une rotation

Country Status (6)

Country Link
US (1) US4296893A (fr)
EP (1) EP0006874A1 (fr)
DE (1) DE2731092A1 (fr)
FR (1) FR2462688A1 (fr)
GB (1) GB2046884A (fr)
WO (1) WO1979000037A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2396949A1 (fr) * 1977-07-09 1979-02-02 Ballmann Josef Projectile destine a etre notamment tire dans un canon lisse

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JPS56147000A (en) * 1980-04-15 1981-11-14 Nagatoshi Maki Short range shell charging for shot gun with drawn barrel
FR2487063B1 (fr) * 1980-07-18 1986-11-14 Maki Nagatoshi Bourre et projectile pour cartouche de fusil de chasse
US4485742A (en) * 1981-06-05 1984-12-04 Mamo Anthony C Firearm bullet
US4669385A (en) * 1983-09-28 1987-06-02 Nagatoshi Maki Wad for shotgun shotshell
US4549487A (en) * 1983-09-29 1985-10-29 Pocal Industries, Inc. Practice projectile with variable range
US5381736A (en) * 1994-01-24 1995-01-17 Kalcic; Frank Recoil reducing bullet
US5841058A (en) * 1996-01-26 1998-11-24 Manis; John Robert Firearms
EP1092122A4 (fr) * 1998-06-30 2001-12-19 Primex Tech Inc Sabot faible rotation
US6085660A (en) * 1998-09-10 2000-07-11 Primex Technologies, Inc. Low spin sabot
RU2242702C2 (ru) * 2002-12-15 2004-12-20 Тарасенко Алексей Владимирович Газовый турбостабилизатор
US20080254705A1 (en) * 2007-04-16 2008-10-16 Southwest Research Institute Dispensing Device
DE102007052938B3 (de) 2007-11-02 2009-04-16 Jallcom Holdings Ltd. Geschoss mit einen Drall erzeugenden Strömungskanälen
DE102007052939B3 (de) 2007-11-02 2009-01-29 Jallcom Holdings Ltd. Munition zum Verschießen aus einem glatten Rohr
US8640624B1 (en) * 2011-12-21 2014-02-04 The United States Of America As Represented By The Secretary Of The Army Low collateral damage air defense projectile
US8893621B1 (en) * 2013-12-07 2014-11-25 Rolando Escobar Projectile
US9885553B2 (en) * 2014-01-02 2018-02-06 Keith Allen Langenbeck Hollow tube projectiles and launch systems thereof
US11867487B1 (en) * 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

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DE298588C (fr) *
GB172710A (en) * 1920-09-07 1921-12-07 Joseph Huggins Brittain Improvements in or relating to means for enabling shot, shrapnel and high explosive shells to be fired from smooth bore guns, cannons and mortars
US2369924A (en) * 1941-10-20 1945-02-20 Sittig Conrad Explosive projectile
FR1011653A (fr) * 1949-02-25 1952-06-25 S E R A M Dispositifs de lancement et de stabilisation des fusées
US3058423A (en) * 1959-09-23 1962-10-16 Creston F Laager Spin, tangential device for projectiles
GB975086A (en) * 1961-03-01 1964-11-11 Dynamit Nobel Ag Improvements in or relating to projectiles
US3419230A (en) * 1966-04-14 1968-12-31 Mb Assoc Nozzle
FR2237169A1 (en) * 1972-07-04 1975-02-07 Rheinmetall Gmbh Gun projectile stabilising system - projectile has pair of guide rings with rifling holes or grooves

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US2559955A (en) * 1946-11-26 1951-07-10 Harlow H Hartwell Projectile
NL6514247A (fr) * 1964-12-22 1966-06-23
US3398682A (en) * 1966-09-14 1968-08-27 Michael F. Abela Spinning projectile
CH520316A (de) * 1970-02-27 1972-03-15 Oerlikon Buehrle Ag Drallstabilisiertes Raketengeschoss
CH574095A5 (fr) * 1973-12-21 1976-03-31 Oerlikon Buehrle Ag
US4063511A (en) * 1976-07-21 1977-12-20 Bullard James M Spinning shot gun projectile

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE298588C (fr) *
GB172710A (en) * 1920-09-07 1921-12-07 Joseph Huggins Brittain Improvements in or relating to means for enabling shot, shrapnel and high explosive shells to be fired from smooth bore guns, cannons and mortars
US2369924A (en) * 1941-10-20 1945-02-20 Sittig Conrad Explosive projectile
FR1011653A (fr) * 1949-02-25 1952-06-25 S E R A M Dispositifs de lancement et de stabilisation des fusées
US3058423A (en) * 1959-09-23 1962-10-16 Creston F Laager Spin, tangential device for projectiles
GB975086A (en) * 1961-03-01 1964-11-11 Dynamit Nobel Ag Improvements in or relating to projectiles
US3419230A (en) * 1966-04-14 1968-12-31 Mb Assoc Nozzle
FR2237169A1 (en) * 1972-07-04 1975-02-07 Rheinmetall Gmbh Gun projectile stabilising system - projectile has pair of guide rings with rifling holes or grooves

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2396949A1 (fr) * 1977-07-09 1979-02-02 Ballmann Josef Projectile destine a etre notamment tire dans un canon lisse

Also Published As

Publication number Publication date
GB2046884A (en) 1980-11-19
FR2462688A1 (fr) 1981-02-13
EP0006874A1 (fr) 1980-01-23
DE2731092A1 (de) 1979-01-25
US4296893A (en) 1981-10-27

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